US20160208618A1 - Cored airfoil platform with outlet slots - Google Patents
Cored airfoil platform with outlet slots Download PDFInfo
- Publication number
- US20160208618A1 US20160208618A1 US14/600,048 US201514600048A US2016208618A1 US 20160208618 A1 US20160208618 A1 US 20160208618A1 US 201514600048 A US201514600048 A US 201514600048A US 2016208618 A1 US2016208618 A1 US 2016208618A1
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- United States
- Prior art keywords
- airfoil
- platform
- recited
- outlet slots
- cooling
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/21—Manufacture essentially without removing material by casting
- F05D2230/211—Manufacture essentially without removing material by casting by precision casting, e.g. microfusing or investment casting
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
- F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- This invention was made with government support under contract number FA8650-09-D-2923-0021 awarded by the United States Air Force. The government has certain rights in the invention.
- Gas turbine engine airfoils, such as turbine blades and turbine vanes, can be fabricated by investment casting. For instance, in investment casting, a ceramic or refractory metal core is arranged in a mold and coated with a wax material, which provides a desired shape. The wax material is then coated with ceramic slurry that is hardened into a shell. The wax is melted out of the shell and molten metal is then poured into the remaining cavity. The metal solidifies to form the airfoil. The core is then removed, leaving internal passages within the airfoil. Typically, the passages are used for cooling the airfoil.
- An airfoil according to an example of the present disclosure includes a platform including platform leading and trailing ends, lateral side faces, and inner and outer faces. An airfoil portion extends outwardly from the inner face of the platform. The platform includes a cooling passage having an inlet at a forward location, outlet slots at the platform trailing end, and an intermediate passage portion extending from the inlet to the outlet slots. The intermediate passage portion includes a common manifold region that feeds the outlet slots.
- In a further embodiment of any of the foregoing embodiments, the cooling passage is relatively wider in a lateral direction between the lateral side faces than in a thickness direction between the inner and outer faces.
- In a further embodiment of any of the foregoing embodiments, the manifold region includes pedestals.
- In a further embodiment of any of the foregoing embodiments, the manifold region includes elongated ribs.
- In a further embodiment of any of the foregoing embodiments, the outlet slots open at the inner face.
- In a further embodiment of any of the foregoing embodiments, the outlet slots open at the outer face.
- In a further embodiment of any of the foregoing embodiments, the outlet slots open at an aft face on the platform trailing end.
- In a further embodiment of any of the foregoing embodiments, the inlet opens at a cavity of the airfoil portion.
- In a further embodiment of any of the foregoing embodiments, the inlet opens at the outer face.
- In a further embodiment of any of the foregoing embodiments, the intermediate passage portion tapers in thickness from the inlet to the outlet slots.
- In a further embodiment of any of the foregoing embodiments, the cooling passage extends over at least 50% of a length of the platform between the platform leading and trailing ends.
- An airfoil according to an example of the present disclosure includes a platform having platform leading and trailing ends, lateral side faces, and inner and outer faces. An airfoil portion extends outwardly from the inner face of the platform. The platform includes a plurality of cooling passages. Each of the cooling passages has an inlet at a forward location and outlet slots at the platform trailing end. The cooling passages are relatively wider in a lateral direction between the lateral side faces than in a thickness direction between the inner and outer faces.
- In a further embodiment of any of the foregoing embodiments, the platform includes a rib that is elongated in a length direction between the platform leading and trailing ends, the rib diving two of the cooling passages.
- In a further embodiment of any of the foregoing embodiments, the rib is approximately midway between the lateral side faces.
- In a further embodiment of any of the foregoing embodiments, the rib is closer in proximity to one of the lateral side faces than the other.
- In a further embodiment of any of the foregoing embodiments, the cooling passages occupy at least 90% of the distance between the lateral side faces.
- In a further embodiment of any of the foregoing embodiments, the outlet slots open at the inner face.
- In a further embodiment of any of the foregoing embodiments, the outlet slots open at the outer face.
- In a further embodiment of any of the foregoing embodiments, the outlet slots open at an aft face on the platform trailing end.
- The various features and advantages of the present disclosure will become apparent to those skilled in the art from the following detailed description. The drawings that accompany the detailed description can be briefly described as follows.
-
FIG. 1 illustrates an example airfoil that has a plurality of cooling passages with outlet slots at the trailing end of the platform. -
FIG. 2 is a sectional view through the platform of the airfoil ofFIG. 1 . -
FIG. 3 is a view of the trailing end of the platform of the airfoil inFIG. 1 . -
FIG. 4 illustrates casting cores that can be used to form the cooling passages in the platform of the airfoil ofFIG. 1 . -
FIG. 5 illustrates a side view of one of the cores ofFIG. 4 . -
FIG. 6 illustrates a modified core with an end that turns up such that the outlet slots formed will open at an outer face of the platform. -
FIG. 7 illustrates a modified core with an end that turns down such that the outlet slots formed will open at an inner face of the platform. -
FIG. 8 shows discharging cooling air through an aft face at the trailing end of an airfoil platform to impinge on a downstream seal. -
FIG. 9 shows discharging cooling air through an outer face at the trailing end of an airfoil platform into a cavity adjacent the airfoil and a downstream seal. -
FIG. 10 shows discharging cooling air through an inner face at the trailing end of an airfoil platform to provide film cooling of the platform and at least a portion of a downstream seal. -
FIG. 11A illustrates another example airfoil, with cores that form a plurality of cooling passages with inlets that open to an airfoil cavity. -
FIG. 11B illustrates the airfoil ofFIG. 11A , without the cores. -
FIG. 12 illustrates casting cores that can be used to form cooling passages in a platform. -
FIG. 13 illustrates the position of the metal rib that separatescores -
FIG. 1 illustrates anexample airfoil 20. In this example, theairfoil 20 is depicted as a static vane and can be used in a gas turbine engine turbine section. Although the examples herein may be described in connection with the static vane, it is to be understood that this disclosure is also applicable to rotatable blades. - in this example, the
airfoil 20 includes aplatform 22 and anairfoil portion 24 that extends outwardly from theplatform 22. For an airfoil vane, there is also anadditional platform 26 at the opposed end of theairfoil portion 24. When mounted in an engine or turbomachine, theplatform 22 is a radially outer platform and theplatform 26 is a radially inner platform. The examples herein could also be applied to theinner platform 26. - The
platform 22 includes platform leading and trailing ends 28/30, lateral side faces 32/34, and inner andouter faces 36/38. Theairfoil portion 24 extends outwardly from theinner face 36. Theairfoil portion 24 includes airfoil leading and trailing ends 40/42 andside walls 44/46 that join the airfoil leading and trailing ends 40/42. - The
platform 22 includes a plurality ofcooling passages 48/50. Although there are twodistinct cooling passages 48/50 in this example, modified examples could have only a single one of thecooling passages 48/50 or a single combined cooling passage. - In
FIG. 1 , castingcores 52 are depicted in theairfoil 20 where thecooling passages 48/50 are formed upon removal of thecores 52. Although each core 52 is shown as a single piece, thecores 52 could alternatively be two or more pieces to form thecooling passages 48/50.FIG. 2 also illustrates a cross-section of the platform according to the section line inFIG. 1 , to depict the geometry of thecooling passages 48/50. Each of thecooling passages 48/50 has aninlet 54 at a forward location, relative to the platform leading and trailing ends 28/30. In this example, theinlet 54 is at least even with theairfoil portion 24. That is, in the axial direction from theplatform trailing end 30 to theplatform leading end 28, the location of theinlets 54 is at least axially aligned with theairfoil 24 or is forward of theairfoil portion 24. - The
cooling passages 48/50 each also includeoutlet slots 56, which can also be seen, in-part, in the view of the trailingend 30 shown inFIG. 3 . In one example, theoutlet slots 56 diverge to the surface to diffuse cooling air upon discharge. Additionally or alternatively, theoutlet slots 56 can be angled circumferentially and/or radially to adjust mixing of the air into the core gas stream. -
Intermediate passage portions 58 ofcooling passages 48/50 extend from therespective inlets 54 to theoutlet slots 56. Each of theintermediate passage portions 58 includes a common manifold region 60 that feeds theoutlet slots 56. - In this example, the
cooling passages 48/50 are relatively wider in a lateral direction, represented at LD inFIG. 2 , between the lateral side faces 32/34 than in a thickness direction, represented at TD inFIG. 1 , between the inner andouter faces 36/38. In one further example, thecooling passages 48/50 occupy at least 90% of the lateral distance at the maximum width of thecooling passages 48/50, represented at D1 inFIG. 2 , between thelateral sides 32/34. Thus, thecooling passages 48/50 are relatively broad, thin passages that thus facilitate internal cooling of theplatform 22. - The
airfoil 20 is fabricated by investment casting a metallic alloy in an investment mold around thecores 52, which are also individually shown inFIG. 4 . Each of thecores 52 include aprintout portion 52 a that facilitates supporting the cores in the mold and also serves to form theinlets 54 of thecooling passages 48/50. As can be appreciated, thecores 52 include sections that correspond to the above-described portions of thecooling passages 48/50 with regard to theinlets 54,outlet slots 56, andintermediate passage portions 58. The corresponding sections of thecores 52 are designated with the same numerals of the cooling passages but with a prime (′). -
FIG. 5 shows a side view of one of thecores 52. In this example, the core 52 tapers in thickness along the length from theprintout 52 a, which forms theinlet 54, to theoutlet slots 56′. Thus, thecooling passage 48/50 also taper in thickness between theinlet 54 and theoutlet slots 56. - In this example, the end of the core 52 with the
outlet slots 56′ is substantially linear such that theoutlet slots 56 of thecooling passages 48/50 open at anaft face 62 on the platform trailing end 30 (FIG. 3 ).FIG. 6 illustrates a modifiedexample core 152 in which the end with theoutlet slots 56′ turns upwards such that theoutlet slots 56 of thecooling passages 48/50 open at theouter face 38 of theplatform 22.FIG. 7 illustrates anotherexample core 252 in which the end with theoutlet slots 56′ turns downward such that theoutlet slots 56 of thecooling passages 48/50 open at theinner face 36 of theplatform 22. Thus, in one further example, there can be a family ofcores 52/152/252 that have similar or identical geometry with the exception of the ends with theoutlet slots 56′. During fabrication of theairfoil 20, one of thecores 52/152/252 can be selected in accordance with cooling performance requirements of theairfoil 20 and downstream components that may be cooled using the discharged cooling air from theoutlet slots 56. - For example, the
airfoil 20 is shown inFIG. 8 in a location in an engine that is axially forward of aseal 70 that is supported bycase elements core 52 was used to form theoutlet slots 56 and thus theoutlet slots 56 open at theaft face 62 of the trailingend 30. Cooling air, represented at CA inFIG. 8 , is discharged through theoutlet slots 56 and impinges upon the forward edge of theseal 70 to thus provide cooling to that forward edge. -
FIG. 9 illustrates another example in which thecore 152 was used to form theoutlet slots 56. In this example, the cooling air CA is thus discharged outwardly toward acavity 74 between thecase elements cavity 74. -
FIG. 10 illustrates another example in which thecore 252 was used to form theoutlet slots 56. Thus, the cooling air CA is discharged through theinner face 36 into the main gas path and serves to film cool the trailingend 30 of theplatform 22 and also theseal 70. Accordingly, depending on the selectedcore 52/152/252, the outlet slots 65 can serve multi-purposes. -
FIG. 11A illustrates another example airfoil 120 with cores, andFIG. 11B illustrates the airfoil 120 without cores. The airfoil 120 is substantially similar to theairfoil 20 but in theairfoil 20 theinlets 54 open at theouter face 38 of theplatform 22 such that the cooling air is directly provided from a source of cooling air, typically a compressor, into thecooling passages 48/50. In the airfoil 120, theinlets 154 open at acavity 24 a of theairfoil portion 24. The cooling air is thus provided into thecooling passages 48/50 from thecavity 24 a. -
FIG. 12 illustrates a further example of anothercore 352. In this example, the manifold region 60 of theintermediate passage portion 58 includespedestals 80′ that will form corresponding pedestals within thecooling passages 48/50. The pedestals serve to mix and/or meter the cooling air as it flows through the cooling passage. Alternatively or in addition to thepedestals 80′, as shown in anotherexample core 452, the manifold region 60 can includeribs 82′ that form corresponding ribs in thecooling passages 48/50. For example, the ribs may be used to guide or direct flow of the cooling air through the common manifold region 60 into theoutlet slots 56. -
FIG. 13 illustratesfurther example cores 552 a/552 b. For example, the cores 52 (FIG. 4 ) are substantially symmetric such that there was a dividing rib 90 (FIG. 2 ) that separated thecooling passages 48/50. Thus, in that example, there would be a relatively equal flow of cooling air passing through both coolingpassages 48/50. In contrast, thecores rib 90′ that will form a corresponding rib in the airfoil is shifted laterally to be nearer to one of the lateral sides 32/34 of theplatform 22. Thus, the corresponding manifold region of the core 552 b will be relatively larger than the manifold region of the core 552 a. For example, the lateral location of therib portion 90′ can be shifted toward the side that has greater cooling requirements. For instance, the cooling air that flows through the smaller cooling passage that is formed by the core 552 a obtains less heat while flowing through theplatform 22 and is thus cooler upon discharge from theplatform 22 than cooling air discharged from the relatively larger cooling passage corresponding to thecore 552 b. That is, the cooling air discharged from the cooling passage corresponding to the core 552 a is relatively cooler and thus can more effectively cool the trailingend 30 of the platform and downstream components, such as thecavity 74 and/orseal 70. - Although a combination of features is shown in the illustrated examples, not all of them need to be combined to realize the benefits of various embodiments of this disclosure. In other words, a system designed according to an embodiment of this disclosure will not necessarily include all of the features shown in any one of the Figures or all of the portions schematically shown in the Figures. Moreover, selected features of one example embodiment may be combined with selected features of other example embodiments.
- The preceding description is exemplary rather than limiting in nature. Variations and modifications to the disclosed examples may become apparent to those skilled in the art that do not necessarily depart from the essence of this disclosure. The scope of legal protection given to this disclosure can only be determined by studying the following claims.
Claims (19)
Priority Applications (3)
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US14/600,048 US10041357B2 (en) | 2015-01-20 | 2015-01-20 | Cored airfoil platform with outlet slots |
EP16152007.7A EP3051065B1 (en) | 2015-01-20 | 2016-01-20 | Cored airfoil platform with outlet slots |
US16/049,987 US10808549B2 (en) | 2015-01-20 | 2018-07-31 | Cored airfoil platform with outlet slots |
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US14/600,048 US10041357B2 (en) | 2015-01-20 | 2015-01-20 | Cored airfoil platform with outlet slots |
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US16/049,987 Continuation US10808549B2 (en) | 2015-01-20 | 2018-07-31 | Cored airfoil platform with outlet slots |
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US16/049,987 Active 2035-06-04 US10808549B2 (en) | 2015-01-20 | 2018-07-31 | Cored airfoil platform with outlet slots |
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US11236625B2 (en) * | 2017-06-07 | 2022-02-01 | General Electric Company | Method of making a cooled airfoil assembly for a turbine engine |
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JP2000220404A (en) | 1999-01-28 | 2000-08-08 | Toshiba Corp | Gas turbine cooling blade |
GB2402442B (en) | 2003-06-04 | 2006-05-31 | Rolls Royce Plc | Cooled nozzled guide vane or turbine rotor blade platform |
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GB201016423D0 (en) | 2010-09-30 | 2010-11-17 | Rolls Royce Plc | Cooled rotor blade |
US8511995B1 (en) | 2010-11-22 | 2013-08-20 | Florida Turbine Technologies, Inc. | Turbine blade with platform cooling |
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- 2015-01-20 US US14/600,048 patent/US10041357B2/en active Active
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2016
- 2016-01-20 EP EP16152007.7A patent/EP3051065B1/en active Active
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- 2018-07-31 US US16/049,987 patent/US10808549B2/en active Active
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US20090028692A1 (en) * | 2007-07-24 | 2009-01-29 | United Technologies Corp. | Systems and Methods for Providing Vane Platform Cooling |
US20110044795A1 (en) * | 2009-08-18 | 2011-02-24 | Chon Young H | Turbine vane platform leading edge cooling holes |
US20130251508A1 (en) * | 2012-03-21 | 2013-09-26 | Marc Tardif | Dual-use of cooling air for turbine vane and method |
US20140047843A1 (en) * | 2012-08-15 | 2014-02-20 | Michael Leslie Clyde Papple | Platform cooling circuit for a gas turbine engine component |
Also Published As
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EP3051065B1 (en) | 2021-10-06 |
US10041357B2 (en) | 2018-08-07 |
EP3051065A1 (en) | 2016-08-03 |
US20180355731A1 (en) | 2018-12-13 |
US10808549B2 (en) | 2020-10-20 |
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